Splitter nose with plasma de-icing for axial turbine engine compressor

Abstract

The invention deals with a splitter nose delimiting the inlet of a low-pressure compressor of an axial turbine engine. The splitter nose comprises a separation surface with an upstream circular edge suitable for separating a flow entering into the turbine engine into a primary flow and a secondary flow, and a plasma de-icing device. The device comprises two annular layers of dielectric material (42; 44) partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shroud which supports blades, an electrode delimiting the primary flow. The device generates plasmas (46; 48; 50) opposing the presence of ice on the partitions of the splitter nose. The invention also deals with a turbine engine with a splitter nose that is provided with a de-icing system downstream of the fan.

What is claimed is: 
     
       1. An axial turbine engine compressor, said compressor comprising
 a splitter nose, the splitter nose comprising:
 a separation surface with an upstream circular edge, intended to split a flow entering into the turbine engine into a primary annular flow and a secondary annular flow wherein the separation surface comprises an inner annular portion intended to delimit the primary flow, an outer annular portion intended to delimit the secondary flow and the upstream circular edge linking the inner annular portion to the outer annular portion; 
 a first layer of dielectric material partially forming the separation surface; 
 a first electrode which partially forms the separation surface and which is adapted to form a plasma in combination with the first dielectric layer in order to de-ice the separation surface, the first electrode being arranged on the upstream circular edge, 
 a second layer of dielectric material, distinct from the first layer of dielectric material, the second layer of dielectric material having a tubular portion; and 
 a second electrode separated from the first electrode by the first layer of dielectric material, the second electrode being configured to be able to form a plasma on the separation surface in combination with the second layer of dielectric material, 
 wherein the first and second dielectric layers are separated axially by an annular groove forming an axial circular gap, which can allow for a relative movement between the first electrode and the second electrode. 
 
 
     
     
       2. The axial turbine engine compressor in accordance with  claim 1 , wherein the compressor comprises;
 an outer wall on which the first layer of dielectric material is arranged; and 
 an outer shroud and an annular row of stator blades extending radially inwards from the outer shroud, wherein the second layer of dielectric material is arranged on the outer shroud. 
 
     
     
       3. The axial turbine engine compressor in accordance with  claim 2 , wherein the outer wall is inwardly in contact with the second layer of dielectric material. 
     
     
       4. The axial turbine engine compressor in accordance with  claim 1 , wherein the first and second layers of dielectric material are formed by a respective organic matrix of a composite material. 
     
     
       5. The axial turbine engine compressor in accordance with  claim 1 , wherein the layers of dielectric material each have a form of revolution with a profile of revolution about the axis of rotation, the first layer of dielectric material being upstream the second layer of dielectric material and the first layer of dielectric material having a profile of revolution radially higher than the profile of revolution of the second layer of dielectric material. 
     
     
       6. The axial turbine engine compressor in accordance with  claim 1 , wherein the nose comprises at least four electrodes distributed in two sets of electrodes configured to be able to generate at least two circular plasmas to de-ice the separation surface, each set of electrodes being separated by a respective layer amongst the first and second layers of dielectric material. 
     
     
       7. The axial turbine engine compressor in accordance with  claim 1 , wherein the first and second layers of dielectric material are U-shaped and cover upstreamingly an outer wall and an outer shroud respectively. 
     
     
       8. The axial turbine engine compressor in accordance with  claim 7 , wherein the outer wall is inwardly in contact with the second layer of dielectric material. 
     
     
       9. The axial turbine engine compressor in accordance with  claim 1 , wherein the first electrode is configured to generate a plasma which flows radially outwardly and inwardly from the first electrode, and the second electrode is configured to form a plasma which flows axially downstream from the second electrode. 
     
     
       10. The axial turbine engine compressor in accordance with  claim 1  wherein the compressor comprises:
 an outer wall on which the first layer of dielectric material is arranged, the first layer of dielectric material being arranged between the first electrode and the outer wall, such that the first electrode and the outer wall form a first set of electrodes generating plasma. 
 
     
     
       11. The axial turbine engine compressor in accordance with  claim 1  wherein the compressor comprises:
 an outer shroud and an annular row of stator blades extending radially inwards from the outer shroud, wherein the second layer of dielectric material is arranged between the outer shroud and the second electrode, such that the second electrode and the outer shroud form a second set of electrodes generating plasma.